AG19 (ag19-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG19 (ag19-il) Reynolds number: 50,000 Max Cl/Cd: 37.1 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag19-il-50000-n5.txt Download as CSV file: xf-ag19-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG19
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5328 0.11368 0.10686 0.0138 1.0000 0.0876
-8.250 -0.5343 0.11143 0.10470 0.0098 1.0000 0.0909
-8.000 -0.5370 0.10933 0.10271 0.0045 1.0000 0.0918
-7.750 -0.5277 0.10440 0.09784 0.0044 1.0000 0.0928
-7.500 -0.5165 0.09990 0.09335 0.0053 1.0000 0.0945
-7.250 -0.5077 0.09607 0.08956 0.0038 1.0000 0.0961
-7.000 -0.4986 0.09224 0.08577 0.0011 1.0000 0.0975
-6.750 -0.4883 0.08823 0.08179 -0.0025 1.0000 0.0978
-6.500 -0.4679 0.08010 0.07354 -0.0120 1.0000 0.0494
-6.250 -0.4542 0.07554 0.06899 -0.0152 1.0000 0.0463
-5.750 -0.4053 0.06231 0.05540 -0.0323 1.0000 0.0389
-5.500 -0.3836 0.05724 0.05015 -0.0363 1.0000 0.0390
-5.250 -0.3597 0.05213 0.04480 -0.0405 1.0000 0.0395
-5.000 -0.3436 0.04926 0.04201 -0.0407 1.0000 0.0424
-4.750 -0.3160 0.04434 0.03664 -0.0444 1.0000 0.0422
-4.500 -0.2861 0.03937 0.03113 -0.0475 1.0000 0.0413
-4.250 -0.2566 0.03519 0.02635 -0.0494 1.0000 0.0411
-4.000 -0.2281 0.03180 0.02246 -0.0505 1.0000 0.0417
-3.750 -0.1998 0.02894 0.01913 -0.0509 1.0000 0.0431
-3.500 -0.1717 0.02664 0.01640 -0.0511 1.0000 0.0471
-3.250 -0.1434 0.02457 0.01383 -0.0509 1.0000 0.0535
-3.000 -0.1167 0.02277 0.01184 -0.0504 1.0000 0.0589
-2.750 -0.0901 0.02119 0.01000 -0.0496 1.0000 0.0677
-2.500 -0.0634 0.01997 0.00864 -0.0492 1.0000 0.0864
-2.250 -0.0356 0.01874 0.00737 -0.0490 1.0000 0.1199
-2.000 -0.0077 0.01733 0.00639 -0.0492 1.0000 0.2041
-1.750 0.0175 0.01584 0.00589 -0.0491 1.0000 0.4175
-1.500 0.0330 0.01385 0.00544 -0.0450 1.0000 0.9564
-1.250 0.0591 0.01385 0.00493 -0.0446 1.0000 1.0000
-1.000 0.0850 0.01390 0.00461 -0.0444 1.0000 1.0000
-0.750 0.1106 0.01396 0.00439 -0.0441 1.0000 1.0000
-0.500 0.1360 0.01405 0.00425 -0.0438 1.0000 1.0000
-0.250 0.1610 0.01417 0.00417 -0.0435 1.0000 1.0000
0.000 0.1858 0.01431 0.00414 -0.0433 1.0000 1.0000
0.250 0.2103 0.01448 0.00420 -0.0430 1.0000 1.0000
0.500 0.2346 0.01470 0.00433 -0.0428 1.0000 1.0000
0.750 0.2586 0.01495 0.00453 -0.0427 1.0000 1.0000
1.000 0.2924 0.01525 0.00480 -0.0446 0.9908 1.0000
1.250 0.3430 0.01550 0.00504 -0.0494 0.9663 1.0000
1.500 0.3911 0.01566 0.00525 -0.0534 0.9398 1.0000
1.750 0.4336 0.01578 0.00543 -0.0558 0.9092 1.0000
2.000 0.4725 0.01588 0.00562 -0.0573 0.8756 1.0000
2.250 0.5062 0.01599 0.00577 -0.0575 0.8377 1.0000
2.500 0.5361 0.01613 0.00591 -0.0568 0.7967 1.0000
2.750 0.5629 0.01631 0.00605 -0.0554 0.7527 1.0000
3.000 0.5876 0.01656 0.00624 -0.0536 0.7052 1.0000
3.250 0.6114 0.01688 0.00653 -0.0518 0.6545 1.0000
3.500 0.6347 0.01728 0.00679 -0.0500 0.6006 1.0000
3.750 0.6577 0.01776 0.00711 -0.0484 0.5457 1.0000
4.000 0.6808 0.01835 0.00752 -0.0469 0.4915 1.0000
4.250 0.7040 0.01901 0.00802 -0.0458 0.4398 1.0000
4.500 0.7273 0.01976 0.00871 -0.0447 0.3926 1.0000
4.750 0.7513 0.02056 0.00942 -0.0440 0.3484 1.0000
5.000 0.7754 0.02142 0.01021 -0.0434 0.3079 1.0000
5.250 0.7994 0.02236 0.01108 -0.0428 0.2717 1.0000
5.500 0.8236 0.02333 0.01209 -0.0423 0.2373 1.0000
5.750 0.8472 0.02439 0.01324 -0.0417 0.2071 1.0000
6.000 0.8707 0.02555 0.01444 -0.0410 0.1803 1.0000
6.250 0.8940 0.02682 0.01580 -0.0404 0.1565 1.0000
6.500 0.9166 0.02818 0.01719 -0.0397 0.1358 1.0000
6.750 0.9394 0.02972 0.01894 -0.0389 0.1170 1.0000
7.000 0.9613 0.03141 0.02077 -0.0382 0.1010 1.0000
7.250 0.9822 0.03318 0.02267 -0.0374 0.0865 1.0000
7.500 1.0036 0.03560 0.02554 -0.0364 0.0758 1.0000
7.750 1.0226 0.03775 0.02799 -0.0357 0.0641 1.0000
8.000 1.0409 0.04077 0.03124 -0.0347 0.0581 1.0000
8.250 1.0570 0.04424 0.03533 -0.0337 0.0519 1.0000
8.500 1.0700 0.04711 0.03843 -0.0331 0.0461 1.0000
8.750 1.0777 0.05195 0.04400 -0.0322 0.0431 1.0000
9.000 1.0805 0.05700 0.04960 -0.0316 0.0415 1.0000
9.250 1.0778 0.06220 0.05525 -0.0315 0.0405 1.0000
9.500 1.0692 0.06759 0.06101 -0.0318 0.0399 1.0000
9.750 1.0522 0.07348 0.06719 -0.0332 0.0402 1.0000
10.000 1.0285 0.08016 0.07405 -0.0366 0.0410 1.0000
10.250 1.0046 0.08887 0.08284 -0.0436 0.0422 1.0000
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Polar data table (+)
Polar graphs
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